Application of the dynamic stiffness method in the vibration analysis of stiffened composite plates (original) (raw)
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Composite Structures, 2017
The dynamic stiffness elements based on the HSDT and FSDT (and the corresponding dynamic stiffness matrices of a laminated composite plate) have been implemented into the original MATLAB code, and a variety of numerical investigations is performed in this paper. The obtained results are validated against the exact and numerical solutions or the experimental data from the literature. In the absence of the analytical solutions, the numerical solutions obtained by using the Abaqus software are used. Excellent agreement is achieved against the existing exact solutions. After the detail convergence study considering both low and high modes of vibration, the effects of the plate side-tothickness and orthotropy ratios, as well as the influence of boundary conditions, have been discussed by comparing the proposed models with the exact Levy-type solutions from the literature. A variety of new results for non-special boundary conditions is provided. Two additional examples of a completely free laminated composite plate undergoing free vibrations are provided and the results are validated against the experiment. Finally, the analyses considering the Z-and U-shaped composite plate assemblies with various boundary conditions are provided as a benchmark for future research.
Composite Structures, 2017
The dynamic stiffness elements based on the HSDT and FSDT (and the corresponding dynamic stiffness matrices of a laminated composite plate) have been implemented into the original MATLAB code, and a variety of numerical investigations is performed in this paper. The obtained results are validated against the exact and numerical solutions or the experimental data from the literature. In the absence of the analytical solutions, the numerical solutions obtained by using the Abaqus software are used. Excellent agreement is achieved against the existing exact solutions. After the detail convergence study considering both low and high modes of vibration, the effects of the plate side-tothickness and orthotropy ratios, as well as the influence of boundary conditions, have been discussed by comparing the proposed models with the exact Levy-type solutions from the literature. A variety of new results for non-special boundary conditions is provided. Two additional examples of a completely free laminated composite plate undergoing free vibrations are provided and the results are validated against the experiment. Finally, the analyses considering the Z-and U-shaped composite plate assemblies with various boundary conditions are provided as a benchmark for future research.
Vietnam Journal of Mechanics, 2013
This research presents a new model for vibration analysis of thick laminated plates on a non-homogeneous elastic foundation by the Dynamic Stiffness Method(DSM). The non-homogeneous foundation consists of multi-segment Winkler-type and Pasternak-type elastic foundation. The Dynamic Stiffness Matrices using the First ShearDeformation Theory (FSDT) are constructed for cross-ply thick composite plates. A computer program is written using the present formulation for calculating natural frequencies and harmonic response of composite plates subjected to various types of boundary conditions. Numerical results are validated by comparison with available results in the literature and with Finite Element Method (FEM). Different test cases make evidence the advantages of the present model: higher precision, less data storage, less computing time and studied frequency range extended.
DYNAMIC ANALYSIS OF STIFFENED AND UNSTIFFENED COMPOSITE PLATES
The Iraqi Journal For Mechanical And Material Engineering, 2013
A suggested solution for dynamic analysis of stiffened and un-stiffened laminated plates is presented in this work. The First order laminated plate theory is used. The equations of motion are solved by using the modal analysis of forced vibration for multi degrees of freedom. The applied load for this study aresine, rectangular, expansion, ramp and triangular pulses. The method of applied these loads is centrally and uniformly distributed across the plate. The deflection and stresses for each layer are presented for stiffened and un-stiffened, symmetrical and un-symmetrical, cross ply and angle ply, laminated composite plate with respect to the plate side-to-thickness ratio, aspect ratio, material orthotropy, and lamination scheme, number of layer of laminated plate, number of stiffeners, high to width of stiffener ratio, high of stiffener, the width of stiffener, and the stiffener properties. The results are very close compared with finite elements method using ANSYS program and withReddy 1982.
Free Vibration Analysis of Stiffened Laminated Composite Plates
International Journal of Computer Applications, 2016
Stiffened Laminated composite plates are widely used in the aerospace, civil, marine, and automotive industries due to their high specific stiffness and strength, excellent fatigue resistance, long durability and many other superior properties compared to ordinary plates. In this paper, the effect of stiffener configuration, number of layers and boundary conditions on the free vibration response of stiffened laminated composite plates are examined with respect to natural frequencies and mode shapes. Six rectangular stiffeners configurations models are used with two types of boundary conditions which are simply and clamped supported. Comparative study is conducted to investigate the effect of stiffener configuration, number of layers and boundary conditions on the free vibration response of stiffened laminated composite plates using the finite element system ANSYS16.
This paper represents the laminated plate growing researc to dynamic loading in their working life and vibration affects working life of the structure predict of the free vibratio displacements of each layer are expressed in terms of Layerwise HSDT the thickness. The displacement field of present theory contains nine unknowns, as in the higher order shear deformation finding the analytical solutions. supported cross been obtained by using Layerwise HSDT. It is sh can provide accurate results. comparing it with various available results in the literature. The results show that the present model performs better than all the exist theories. ABSTRACT This paper represents the aminated plate growing researc to dynamic loading in their working life and vibration affects working life of the structure. Layerwise predict of the free vibratio displacements of each layer are expressed in terms of Layerwise HSDT the thickness. The displacement field of present theory contains nine unknowns, as in the higher order shear deformation finding the analytical solutions. supported cross been obtained by using Layerwise HSDT. It is sh can provide accurate results. comparing it with various available results in the literature. The results show that the present model performs better than all the exist heories. This paper represents the aminated plate. As we know that vibration and composite material are two main growing research topics now a days. Almost all the structural components subjected to dynamic loading in their working life and vibration affects working life of the Layerwise Higher Order Shear Deformation Theory (predict of the free vibratio displacements of each layer are expressed in terms of Layerwise HSDT the thickness. The displacement field of present theory contains nine unknowns, as in the higher order shear deformation finding the analytical solutions. supported cross-ply and anti been obtained by using Layerwise HSDT. It is sh can provide accurate results. comparing it with various available results in the literature. The results show that the present model performs better than all the exist IJMET/index.asp This paper represents the investigation As we know that vibration and composite material are two main h topics now a days. Almost all the structural components subjected to dynamic loading in their working life and vibration affects working life of the Higher Order Shear Deformation Theory (predict of the free vibration characteristics of laminated composite plates. displacements of each layer are expressed in terms of Layerwise HSDT the thickness. The displacement field of present theory contains nine unknowns, as in the higher order shear deformation finding the analytical solutions. Non ply and anti-symmetric angle been obtained by using Layerwise HSDT. It is sh can provide accurate results. The accuracy of the present theory is ascertained by comparing it with various available results in the literature. The results show that the present model performs better than all the exist asp 414 investigation on the response of a As we know that vibration and composite material are two main h topics now a days. Almost all the structural components subjected to dynamic loading in their working life and vibration affects working life of the Higher Order Shear Deformation Theory (n characteristics of laminated composite plates. displacements of each layer are expressed in terms of Layerwise HSDT the thickness. The displacement field of present theory contains nine unknowns, as in the higher order shear deformation theory Navier's solution method is used for Non-dimensional fundamental frequencies of simply symmetric angle-ply laminated composite plates have been obtained by using Layerwise HSDT. It is sh The accuracy of the present theory is ascertained by comparing it with various available results in the literature. The results show that the present model performs better than all the exist the response of a As we know that vibration and composite material are two main h topics now a days. Almost all the structural components subjected to dynamic loading in their working life and vibration affects working life of the Higher Order Shear Deformation Theory (n characteristics of laminated composite plates. displacements of each layer are expressed in terms of Layerwise HSDT the thickness. The displacement field of present theory contains nine unknowns, as in theory Navier's solution method is used for dimensional fundamental frequencies of simply-ply laminated composite plates have been obtained by using Layerwise HSDT. It is shown that the present Layerwise HSDT The accuracy of the present theory is ascertained by comparing it with various available results in the literature. The results show that the present model performs better than all the existing higher order shear deformation the response of a symmetric composite As we know that vibration and composite material are two main h topics now a days. Almost all the structural components subjected to dynamic loading in their working life and vibration affects working life of the Higher Order Shear Deformation Theory (HSDT n characteristics of laminated composite plates. displacements of each layer are expressed in terms of Layerwise HSDT the thickness. The displacement field of present theory contains nine unknowns, as in theory Navier's solution method is used for dimensional fundamental frequencies of simply ply laminated composite plates have own that the present Layerwise HSDT The accuracy of the present theory is ascertained by comparing it with various available results in the literature. The results show that the ing higher order shear deformation symmetric composite As we know that vibration and composite material are two main h topics now a days. Almost all the structural components subjected to dynamic loading in their working life and vibration affects working life of the HSDT) is used to n characteristics of laminated composite plates. displacements of each layer are expressed in terms of Layerwise HSDT functions of the thickness. The displacement field of present theory contains nine unknowns, as in theory Navier's solution method is used for dimensional fundamental frequencies of simply ply laminated composite plates have own that the present Layerwise HSDT The accuracy of the present theory is ascertained by comparing it with various available results in the literature. The results show that the ing higher order shear deformation symmetric composite As we know that vibration and composite material are two main h topics now a days. Almost all the structural components subjected to dynamic loading in their working life and vibration affects working life of the is used to The functions of the thickness. The displacement field of present theory contains nine unknowns, as in theory Navier's solution method is used for dimensional fundamental frequencies of simply ply laminated composite plates have own that the present Layerwise HSDT The accuracy of the present theory is ascertained by comparing it with various available results in the literature. The results show that the ing higher order shear deformation
Archive of Applied Mechanics, 2012
A global higher-order shear deformation theory is devised to obtain the governing equations of composite plates under dynamic excitation. The time-harmonic solution leads to an eigenvalue problem for the natural frequencies of plates. The eigenvalue problem for rectangular plates is converted to a set of homogenous algebraic equations using differential quadrature method. The formulation of the problem allows direct application of various boundary conditions. Therefore, rectangular plates with mixed boundary conditions are also considered. To show the validity of results, the fundamental natural frequencies of composite plates with different boundary conditions and those of isotropic plates with mixed boundary conditions are compared against the results available in the literature.
Free-vibration analysis of stiffened laminated plates using higher-order shear deformation theory
Finite Elements in Analysis and Design, 1996
This paper presents the free vibration analysis of stiffened laminated plate using Finite element method. Stiffened laminated plate are commonly employed in the structures of many aerospace vehicles such as aircrafts, rockets, missiles, etc. Therefore it is necessary to determine the structural deformation and vibrational characteristics of such structures where it is desired to have high natural frequencies. The free vibration results obtained by the present finite element model are compared with previous results for the stiffened composite plate. The result shows that the present model for the stiffened plate gives quite accurate results. Effects of the eccentricity, orientation-symmetric and anti-symmetric, angle-ply and cross-ply and boundary condition are also investigated.
Journal of Sound and Vibration, 2016
This paper deals with the free vibration analysis of isotropic plate assemblies using the dynamic stiffness method (DSM) based on the Reddy's higher-order shear deformation theory (HSDT). Using the proposed method, the isotropic rectangular plate assemblies of non-uniform thickness and material properties can be analyzed. The proposed model does not have any restrictions regarding the boundary conditions or the frequency limitations. It enables free vibration analysis of both thin and thick plates, making it advantageous in comparison with the conventional finite element method (FEM) regarding the computational cost and the accuracy of the results. Three coupled Euler-Lagrange equations of motion based on the HSDT have been transformed into two uncoupled equations of motion introducing a boundary layer function. The dynamic stiffness matrix for a completely free rectangular plate element has been derived using the superposition and the projection method. The proposed numerical model has been applied in the free vibration analysis of rectangular plate assemblies. Along with the convergence study, the results for natural frequencies have been validated against the existing data from the literature, the previous results from the authors as well as the results obtained by using the finite element software Abaqus. Excellent agreement has been obtained. Finally, a variety of new results is provided as a benchmark for future investigations.
Eigen-frequency Analysis of Stiffened Laminated Composite Plates Using Finite Elements
This article presents the free vibration responses of stiffened laminated composite plates (SLCP) using finite elements. The SLCP midplane kinematics has been modeled using ABAQUS commercial finite element tool in the framework of first order shear deformation theory. Firstly, the validity of the present model is established by comparing the present eigenfrequency (natural frequency) values with the available benchmark results. Subsequently, the influence of varying eccentricity, depth of the stiffeners and width-to-depth ratio of the stiffener on the natural frequency of SLCP is investigated by solving appropriate numerical examples and findings are discussed in detail.